class RotorStructureBase(Component):
"""
Base class for models that can predict blade deflections
based on load distribution
"""
blade_disps = VarTree(BeamDisplacementsVT(), iotype='out', desc='Blade deflections and rotations')
class AeroElasticSolverBase(Component):
"""
base class for aeroelastic solvers that computes both steady state aerodynamic loads
and structural deflections in a monolithic analysis for a single case
"""
wt = VarTree(AeroelasticHAWTVT(), iotype='in', desc='Turbine definition')
inflow = VarTree(TurbineEnvironmentVT(), iotype='in', desc='Inflow conditions')
oper = VarTree(RotorOperationalData(), iotype='out', desc='Operational data')
rotor_loads = VarTree(RotorLoadsVT(), iotype='out', desc='Rotor torque, power, and thrust')
blade_loads = VarTree(DistributedLoadsVT(), iotype='out', desc='Spanwise load distributions')
blade_disps = VarTree(BeamDisplacementsVT(), iotype='out', desc='Blade deflections and rotations')
class AEsolver(Component):
wt = VarTree(AeroelasticHAWTVT(), iotype='in', desc='Turbine definition')
inflow = VarTree(TurbineEnvironmentVT(), iotype='in', desc='Inflow conditions')
oper = VarTree(RotorOperationalData(), iotype='out', desc='Operational data')
rotor_loads = VarTree(RotorLoadsVT(), iotype='out', desc='Rotor torque, power, and thrust')
blade_loads = VarTree(DistributedLoadsExtVT(), iotype='out', desc='Spanwise load distributions')
blade_disps = VarTree(BeamDisplacementsVT(), iotype='out', desc='Blade deflections and rotations')
def execute(self):
print ''
print 'running aeroelastic analysis ...'
def execute(self):
super(HAWC2SOutputIDO, self).execute()
# hack to get around bug in OpenMDAO that causes
# the outputs to refer to the same object
self.blade_loads = copy.deepcopy(self.blade_loads)
self.blade_disps = copy.deepcopy(self.blade_disps)
self.rotor_loads = copy.deepcopy(self.rotor_loads)
self.oper = copy.deepcopy(self.oper)
data = self.operational_data
self.oper.wsp = data[:, 0]
self.oper.pitch = data[:, 1]
self.oper.rpm = data[:, 2]
data = self.rotor_loads_data
if data.shape[0] == 0:
return
self.rotor_loads.wsp = data[:, 0]
# keeping this for now so I don't break any code relying on this output
self.rotor_loads.rpm = data[:, 9]
self.rotor_loads.pitch = data[:, 8]
self.rotor_loads.P = data[:, 1] * 1000.
self.rotor_loads.Q = data[:, 1] * 1000. / data[:, 9] * 2. * np.pi / 60.
self.rotor_loads.T = data[:, 2] * 1000.
self.rotor_loads.CP = data[:, 3]
self.rotor_loads.CT = data[:, 4]
self.hub_loads.Mx = data[:, 6] * 1000.
self.hub_loads.My = data[:, 7] * 1000.
self.hub_loads.Mz = data[:, 5]
self.blade_disps.tip_pos = np.zeros((self.rotor_loads.wsp.shape[0], 3))
self.blade_disps.tip_rot = np.zeros(self.rotor_loads.wsp.shape[0])
self.blade_loads.loads_array = []
self.blade_disps.disps_array = []
Fx_array = []
Fy_array = []
for i, wsp in enumerate(self.rotor_loads.wsp):
data = self.blade_loads_data[i]
if len(data.shape) == 1:
data = data.reshape(1, data.shape[0])
loads = DistributedLoadsExtVT()
disps = BeamDisplacementsVT()
loads.s = data[:, 0] # / self.blade_length
loads.aoa = data[:, 4] * 180. / np.pi
loads.Ft = data[:, 6]
loads.Fn = data[:, 7]
loads.cl = data[:, 16]
loads.cd = data[:, 17]
loads.cm = data[:, 18]
loads.ct = data[:, 32]
loads.cp = data[:, 33]
loads.v_a = data[:, 26]
loads.v_t = data[:, 27]
Fx_array.append(np.trapz(data[:, 6], x=data[:, 0]))
Fy_array.append(np.trapz(data[:, 7], x=data[:, 0]))
disps.main_axis = data[:, 13:16]
disps.main_axis[:, 2] *= -1.
disps.x = disps.main_axis[:, 0]
disps.y = disps.main_axis[:, 1]
disps.z = disps.main_axis[:, 2]
disps.rot_z = data[:, 28] * 180. / np.pi
self.blade_loads.loads_array.append(loads)
self.blade_disps.disps_array.append(disps)
self.blade_disps.tip_pos[i, :] = disps.main_axis[-1, :]
self.blade_disps.tip_rot[i] = np.interp(0.98, loads.s, data[:, 28] * 180. / np.pi)
self.hub_loads.Fx = np.asarray(Fx_array)
self.hub_loads.Fy = np.asarray(Fy_array)